ChangZheng 6 (CZ-6, or Long March -6 in its translation) is a liquid-propellant, small-load space launch vehicle (SLV) currently developed by China Academy of Launch Vehicle Technology (CALT). The launch vehicle is based on the 2.25m-diameter core stage, which has been developed as a strap-on booster for the CZ-5 family of SLV. The core stage consists of a 120t-thrust YF-100 engine that burns oxygen and kerosene (LOX/Kerosene) propellant, which causes less pollution compared to the UDMH/N2O4 (nitrogen tetroxide) propellant currently in use.

The ChangZheng 6 is designed for small-load launch missions, with a sun-synchronous orbit (SSO) capability of 500kg. The first launch of ChangZheng 6 is scheduled in 2010.

China has started developing the Long March 6 carrier rockets for its space programs, the China National Space Administration announced on its official website.

The Long March 6 rockets will be non-toxic and pollution-free while featuring a number of new technologies used for the first time in China, according to the administration.

The Long March 6 rockets are expected to be ready for blast off in 2013, it said.

The rockets will be designed by the China Aerospace Science and Technology Corporation, developer of the Shenzhou VII spacecraft, from which Chinese aeronauts carried out the country's first space walk in 2008.

The payload capacity of the Long March 6 rockets is not revealed. Neither are specific space programs the rockets are to be involved in.

China aims to set up a simple space lab in 2011 and a manned space station in 2020. It also intends to go further in space and has set its eyes on a moon landing.

ChangZheng 6 (CZ-6, or Long March -6 in its translation) is a liquid-propellant, small-load space launch vehicle (SLV) currently developed by China Academy of Launch Vehicle Technology (CALT). The launch vehicle is based on the 2.25m-diameter core stage, which has been developed as a strap-on booster for the CZ-5 family of SLV. The core stage consists of a 120t-thrust YF-100 engine that burns oxygen and kerosene (LOX/Kerosene) propellant, which causes less pollution compared to the UDMH/N2O4 (nitrogen tetroxide) propellant currently in use.

The ChangZheng 6 is designed for small-load launch missions, with a sun-synchronous orbit (SSO) capability of 500kg. The first launch of ChangZheng 6 is scheduled in 2010.

Last update: 20 February 2009

I can speak a little English.I hope you will understand what I mean.I think there are some wrong in the article.1.CZ-6 is not developed by CALT but SAST(Shanghai Academy of Space Technology).2.The launch vehicle is based on the 3.35m-diameter core stage but not 2.25m-diameter.

I don't think it is a replacement for the KT-1.KT-1 is a solid-propellant launch vehicle and CZ-6 is a liquid-propellant launch vehicle.I think it may be use to launch satellite which has a sun-synchronous orbit(SSO) like CZ-4 and KT-1 is a immature launch vehicle.

I don't think it is a replacement for the KT-1.KT-1 is a solid-propellant launch vehicle and CZ-6 is a liquid-propellant launch vehicle.I think it may be use to launch satellite which has a sun-synchronous orbit(SSO) like CZ-4 and KT-1 is a immature launch vehicle.

I don't think it is a replacement for the KT-1.KT-1 is a solid-propellant launch vehicle and CZ-6 is a liquid-propellant launch vehicle.I think it may be use to launch satellite which has a sun-synchronous orbit(SSO) like CZ-4 and KT-1 is a immature launch vehicle.

1.CZ-6 is not developed by CALT but SAST(Shanghai Academy of Space Technology).

That's correct of course.

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2.The launch vehicle is based on the 3.35m-diameter core stage but not 2.25m-diameter.

I doubt it because we've already seen mentions of CZ-2F/H using the 3.35 m core stage with YF-100 engines. Also, if the payload mass is not misquoted I can't imagine a 3.35 m vehicle with such a low capacity.

Great chart! Is it right to think the "K" stages burn kerosene and the "H" stages burn hydrogen? Also, any guess why there are fins/winglets on the K2-1 when it's used as a strap-on booster? Could they be planning on flying it back for recovery?

On the first chart mentionned by Dmitry_V_home, do we know which one is the LOX/Kerosene engine (top-right image or bottom-left) ? I would say the top-right, because LOX/LH2 looks usually more complex ... but I'm no expert when it comes to propulsion

I read the chart as saying the left engine is kero/LOX, and appears to be a staged combustion design by the ducting going to the combustion chamber from the all-in-a-line turbopump assembly as is typical of Russian practice. Probably equivalent to the RD-191.

The right engine, by default is cryogenic and is a simpler open cycle gas generator with exhaust ducts on either side of the exhaust nozzle, more like the RS-68. I'm guessing the larger duct is from the hydrogen turbopump, which requires more energy.

I doubt it because we've already seen mentions of CZ-2F/H using the 3.35 m core stage with YF-100 engines. Also, if the payload mass is not misquoted I can't imagine a 3.35 m vehicle with such a low capacity.

Only one YF-100 engine in the the 3.35 m core stage of the small launch vehicle, the upper stage is 2.25 m diameter with a 15 tonne thrust YF-115 engine. the payload mass is appropriate with thrust。CZ-2F/H using the 3.35 m core stage with TWO YF-100 engines，while four boosters with ONE YF-100 engine each others, the rocket lift off using six YF-100 engines.

Changzheng 6 is the PRCís new generation liquid-propellant, small-load launch vehicle, currently being developed by the Shanghai Academy of Spaceflight Technology (SAST). The launch vehicle is designed to send at least 500kg payload into the Sun Synchronous Orbit (SSO) of 700km.The launch vehicle is based on a 3.35m diameter core stage, which consists of a single 120t-thrust YF-100 rocket engine. The second stage uses a single 15t-thrust YF-115 engine. Both engines burn an oxygen and kerosene (LOX/Kerosene) propellant. The third stage is 2.25m in diameter and consists of four 1kN-thrust rocket motors.